A modern Second Launch Pad (SLP) was awaiting commissioned in 2005. SLP was to help to increase the frequency of launches from SDSC. The new facility was designed to reduce the occupancy time for the integration and launch.

Sriharikota was known to have been used for at least 358 launches from 1971 to 2008.

TES Indian military surveillance satellite. One launch, 2001.10.22. TES was an imaging satellite equipped with cameras and instruments to test military reconnaissance satellite technology. More...

PROBA European earth land resources satellite. One launch, 2001.10.22. Proba (PRoject for On-Board Autonomy, 1) was a European Space Agency technology development minisatellite with a mass of 94 kg. More...

BIRD German earth land resources satellite. One launch, 2001.10.22. More...

METSAT Indian earth weather satellite. One launch, 2002.09.12. METSAT was an Indian (ISRO) meteorological, geostationary satellite designed to simultaneously obtain atmospheric cloud cover, water vapor, and temperature data. More...

Chandraayan Indian lunar orbiter. One launch, 2008.10.22. First Indian lunar orbiter. It released the MIP impactor. More...

MIP Indian lunar impact probe. One launch, 2008.10.22. Moon Impact Probe, released from Chandraayan-1 in lunar orbit. The MIP fired its own deorbit motor and impacted the moon near the Shackleton Crater at the south pole. More...

Shahab Iranian derivatives of North Korean Nodong 1 intermediate range ballistic missile, evolved incrementally with Russian assistance into a longer-range missile and the first stage of an orbital launch vehicle. More...

Shahab 3 Iranian intermediate range ballistic missile, evolved incrementally with Russian assistance from initial copy of North Korean Nodong 1 into a longer-range missile and the first stage of an orbital launch vehicle. Initial version began flight tests in 1998. More...

GSLV Indian mixed-propulsion orbital launch vehicle for geosynchronous satellites using a Lox/LH2 upper stage developed from Russian technology. More...

GSAT-1 - .
Payload: GramSat. Mass: 1,530 kg (3,370 lb). Nation: India. Agency: ISRO. Program: Insat. Class: Communications. Type: Civilian communications satellite. Spacecraft: Gsat. USAF Sat Cat: 26745 . COSPAR: 2001-015A. Apogee: 35,814 km (22,253 mi). Perigee: 33,825 km (21,017 mi). Inclination: 0.0000 deg. Period: 1,387.00 min. Experimental Rural Communications satellite. Launch delayed following pad abort on March 28. First launch of the Indian GSLV launch vehicle. GSat 1 was an Indian, 1500 kg scaled-dow) test model of a future geosynchronous communications spacecraft with a 440 N ISRO liquid apogee motor, and S-band and C-band ommunications transponders, similar to the Insat-2 satellites. The motor for the cryogenic, hydrogen-oxygen upper stage had been purchased from Russia but the design had never flown in space before. The stage cut off without providing the required delta-V - preliminary analysis revealed a shortfall of 0.5% in the thrust. An attempt was made to reach a usable orbit using the station-keeping motor of the GSAT satellite itself. After a series of burns, GSat 1 ran out of propellant - 10 kg more fuel would have been required to reach a stationary orbit. In the end, the parameters of the drifting (about 13 deg/day) orbit were period 23 hours, apogee 35,665 km, perigee 33,806 km, and inclination 0.99 deg. The fully functional transponders and transmitters on board were deactivated on instructions of the International Telecommunications Union. As of 4 September 2001 located at 54.88 deg E drifting at 13.212 deg E per day. As of 2007 Mar 10 located at 50.16W drifting at 12.778E degrees per day.

Compared to earlier satellites in the Insat series, Edusat used several new technologies. The spacecraft was built around the I-2K standardised spacecraft bus. It had a multiple spot beam antenna with a 1.2 m reflector to direct Ku band spot beams, a dual core bent heat pipe for thermal control, high efficiency multi-junction solar cells and an improved thruster configuration for optimised propellant use for orbit and orientation maintenance. The satellite used radiatively cooled Ku-band Travelling Wave Tube Amplifiers and a dielectrically loaded C-band demultiplexer for its communication payloads. Edusat carried five Ku-band transponders providing spot beams, one Ku-band transponder providing a national beam and six Extended C-band transponders with a national coverage beam. It was to join the Insat system that already provided more than 130 transponders in C-band, Extended C-band and Ku-band for a variety of telecommunication and television services.

First operational flight of launch vehicle. Launch delayed from July, August and September 10. Dry mass 820 kg. As of 2007 Mar 9 located at 73.92E drifting at 0.006W degrees per day.

CartoSat 1 - .
Payload: IRS-P5. Mass: 1,560 kg (3,430 lb). Nation: India. Agency: ISRO. Spacecraft: IRS. USAF Sat Cat: 28649 . COSPAR: 2005-017A. Apogee: 623 km (387 mi). Perigee: 620 km (380 mi). Inclination: 97.9000 deg. Period: 97.10 min. First launch from new second PSLV pad at Sriharikota. Eleventh satellite in the Indian Remote Sensing satellite series, Cartosat-1 carried two panchromatic cameras, one fore-mounted with a tilt of +26 deg and the other aft-mounted with a tilt of -5 deg from the yaw axis. Together they provided black-and-white stereoscopic pictures in the visible region ( 0.50-0.85 micron) of the electromagnetic spectrum with a spatial resolution of 2.5 metre. The cameras covered a swath of 30 km and a solid state memory recorded up to 120 GB of images for downloading when the satellite passed over the Spacecraft Control Centre at Bangalore or ISTRAC stations at Lucknow, Mauritius, Bears Lake in Russia and Biak in Indonesia. Cartosat 1's sun-synchronous orbit crossed the equator at a local time of 10:30. The spacecraft was 3-axis stabilised using reaction wheels, magnetic torquers and hydrazine thrusters. 1100 W of eectrical power was provided by a 5 sq m solar array and two 24 Ah Ni-Cd batteries. Mission life was 5 years. Launch delayed from February, late April. The multispectral satellite had a 2.5-meter resolution camera.

Iranian multiple missile firings - .
Nation: Iran. Apogee: 150 km (90 mi). The Iranians fired at least one Shahab-3 and "dozens of" Shahab-2, Zolfaghar-73, Scud B, Fath-110 and Zelzal missiles in a mass firing demonstration to kick off their Great Prophet 2 military exercise. It marked the first firing of the Shahab 3 by troops on exercise as opposed to a test flight. The Shahab 2 was reported to have demonstrated a 1,400-bomblet cluster bomb warhead.